Wing



Aug-v 9, 1932- E. G. KON-ros 1,870,514

WING

Filed Dec. 18, 195o I ImferW Patented Aug. 9, 1932 PATENT CFFlC- EMMANUEL Gr. KONTOS, OF CHICAGG, ILLINOIS WING Application filed December 18, 1930. Serial No. 503,153.

The invention relates to improvements in flying machines and particularly to improved wings therefor. An object of the invention is to provide improved wings for heavier-than-air flying machines with. automatic stabilizing means. Another object is to provide an'improved wing applicable to any heaver-than-air flying machines, including propelled machines, l@ gliders, or toys.

' Another object is to provide wings of the oharacter'referred to, with means formed on their under side to provide for carrying an increased amount of wing load.

Another object is to provide an improved wing with entering and trailing edges formed to increase stability thereof and minimize air resistance. c Another object is to provide a flying ma- 3 chine with means to preventknose-diving, listing, tail-spinning, or inverted flying, Without resorting to the use of either rudders, elevators, or ailerons.

Another object is to provide wings for a flying machine with imProved means to neutralize the twisting force of the propeller which tends to overcome the stability of the machine and cause it to list.

o y The foregoing and such other objects of 3 the invention as will appear hereinafter as the description proceeds, will be more read ily understood from a perusal of the follow ing specication, reference being had to the M, accompanying drawing, in which:

Fig. l is a plan view of the improved wavy wings.

Fig. 2 is a bottom View of the Wings shown in Fig. 1.

Fig. 3 is an enlarged transverse sectional view o-f the wings, takenon line 3 3 of Fig. ll.

y Fig. 4 is an enlarged fragmentary longitudinal sectional view, taken on line l-Ll of 45 Fig. 1.

Fig. 5 is a bottom view, showing a. wing having its leading and ytrailing edges tapering longitudinally towards the tip.

' Fig. 6 is a fragmentary bottom view of 50 the tipv of a modified form of wing.

rcontrolling elements to function properly 'its under surface that stability is automati-y Fig. 7 is a transverse view similar to Fig. 3, showing a wing of single thickness.

Fig. 8 is a plan view similar to Fig. 1, showing ailerons or elevators attached to the improved wing. 55

Fig. 9 is a transverse sectional view, in perspective, of the tip of a modified form of wing. l

Fig. 10 is a diagrammatic view,illustrat-v ing the application of the improved wings '50 to a kdihedral monoplane.

Fig. 11 is a view similar to Fig. l0, illustrating another application of the improved wings.

In known types of power propelled heavier-than-air flying machines equilibrium and stability are maintained only by the employment and manipulation vof ailerons, elevators, ru'dders, etc. Failure of any of these F may result in the machine slipping, nosedivlng, or tail-spinmng- The improved wavy wing 1s so formed on cally attained and held without manipulation of ailerons, elevators, or rudders, said elements being employed only to change the course of the flying machine from the horizontal. The improved form of wing may be applied to any known type of power n driven flying machine, such as for example, dihedral planes, monoplanes, biplanes, or triplanes. lt also may be applied to gliders, either of the commercial type or toys, and to toy miniature iiying machines employing rubber band motors, or the like.

The improved wings preferably are continuous from tip to tip, as illustrated in Figs. l, 2, 5, and 8, with the tips formed round, as shown. The wing structure preferably consists of the usual spars 1l and ribs 12 having a suitable covering 13, secured thereover, such as for example, fabric or metal. The upper side of the wings may be of any approved practical shape, having its leading and trailing edges l5 and 16, respectively, and tips 1T uniformly tapering downwardly to reduce air resistance. The under side of the wings is cambered longitudinaln ly on each side of the longitudinal center,

tance below the bottom face 19 ofthe lead" ing and trailing edgesdlandA v16,:and thev tips 17. The exact extent of projection of the belly 18, relative to the bottom face'f19, may vary, dependingl upon the, articular application of the wings because, 0r vexam- 4ple, its application toa speed plane .necessitatesfv asmaller belly than whenwapplied ltoV slow. flying planes.

- The principle of forming theA runder side4 of the wings as described, involves-.the'uti- ...lization ofthe air current for stabilizing t-he flyingfmachine. yAir currents entering -beneath the wings along the elevated leading,

`edge 115 naturallyswlngupwardly into the forward'-.longitudinal camber, striking the downwardly curved bellya18fofl-said wing.

.Asfthe aincurrents continue rearwardly bef neath .the bel-ly `18,i they enter into .the rear camber and pass out beneath the elevated -trailingedge 16. This-movementr ofz'tlie air f currents rinsuresanequal lifting force .actng on ,each `side ofy the .longitudinalcenter bf. the wings, thereby balancing :sai d wings von-the longitudinal' center.

.Irrespective of any temporaryposition vof p the wings 'relative to the horizontal, .said

wings, and likewise thevlying machine'at- .tached thereto, .immediately tend. to. assume .lahorizontal-jposition. iTo vary `the course of vthe flying machine, ailerons or elevators. 21, i shown irl-Fig. 8,are provided on` the trailing-edge. of the wings one adjacent each tip.

:These i ailerons preferably extend partly around -the respect-ive Ytips of .the wingsto Amaintain lthe smoothsstrea-m line. 5 The usual. rudder andelevators .(not shownl-.are

f employed for controlling theI course of. flight.

Since the` improved wings insurel automatic.

horizontal, longitudinal,- and .lateralost'abill wings.

sity, failureof...the controls to/operate .the

ailerons, rudder, ory elevators, merely prelevents bringingthe plane out of the horizonital. .-.A.ying machine provided with wings 0f the improved'character cannot nose-dive,

"tail-spin, or slip, due rto the kperfect equili-k brium .insured the plane by said .improved fThe vimproved wing .constructionis tread- -ily applicable to dihedral. wings and,.in such application, as shown in Figs. 5 and 11, itis desirable, but vnot necessary, that the entering andftrailing edges. 15. and v16 ofv the wings taper inwardly ltowards .each roundedtip.

"I liis wing formation minimizes 'thezairsresistance oerd by dihedral Wings. :As-:illusside.

:wings have been shown inthe accom trated in Fig. 6, the double cambered under side of the wings 22 may extend to the rounded tip without curvin therearound.

Where a iying macine of extreme lightness is required, as for example, in scout planes or gliders, Wings 23 (Fig. 7) of single thicknessmay bey provided. The double :camberedundersurace of this style of wing may be identical with either ofthe Wings hereinbefore described; however, no top cov- 'eringlor-.fstmamlineieect is provided. Win

ofthe type shown in Fig. 7 are applicab e for attachment on toys, because they may be stamped or pressed from metal or cardboard and readily secured to' a miniature fuselage.

YAlthonghwm s ofthe various. types .pre- .viously describe are a plicable.to most commonly used forms fdiling-machines,`wings 24, such. as illustratedin'Fi 9`,ihaving aiplurality .of .waves on the. un erside. .alsomay satisfactrilyy be employed. :The .fragment of. `the wing .shownl 1s provided with... a depressed. longitudinal. center 25, .intermediate depressed portions`26 one on on each side of the longitudinal center, anddepressed edges g 27. .The :bottom plane of the' depressed portions... 26 is disposed. a short distance .above ythe/plane loffthedepressed centerL25, and the plane of edges 27 terminatesabove 'theplane ofA portions.. 26. lTheintermedi'ate raised portions v28 and;29. preferably are .in a common: lane, thus-providin a. wing having. a, plura ity of longitudinal y extending I air pocketson itsamder side. .2A wing ofthe type shown .in Fig. 9 may be usedv on toys,`

gliders, .or..da.rts, or a .circularwin having its diametrical section '.thesame as t e transverse section of the wing 'shownmay be pro` vided.

` .Itcan readily be understood that air-cur# Vrents.passfbelovvand strike the underside of any. ofithe types'of wings shown, with s`u b stantially an equal force and velocity on each yside .ofthe longitudinal center, thus prevent- .ing`.flisting, tail-spinning, and nose-diving.

Sincev the air currents are equally distribute Athe equilibrium and the stability of ytheflying machine are maintained without the use of a rudder.-y or ailerons.

..Heretofore, it has been :necessary to 4tilt or elevate one wing of a flying machine 'slightly Vabove Ythe other to overcome 'the .torsional strain of a single propeller. Such torsional strain tends to tilta flying machineand'direct it from its true course. Tliistendency to tilt and misdirectis overcome automatically by employment of the improved Wingsdue to lthe kparticular formation of their under Although exemplary forms of the imprmjedy .n mg drawing and describedrinidetaildn t e oregoing specification, yit isi .toibe understood that the .wing structure may embod certain modifications in detail':"withontzv partingf from the spirit of the invention or the scope of the appended claims.

I claim:

l. A substantially rectangular wing, for a flying machine, having a downwardly flared edge therearound, and means formed in said wing, extending longitudinally thereof below the plane of said edge, to maintain the stability of said wing.

2. A wing for a flying machine, comprising in combination, a frame built of spars and ribs having its marginal edges turned downwardly and a longitudinal enlarged central portion, a covering for said frame, said covering conforming to the shape of said frame to provide a self-balancing wing.

3. A substantially rectangular wing rounded on its ends having a continuous downwardly curved marginal edge, and means formed in said wing extending longitudinally thereof below the plane of said edge to maintain the stability of said wing.

4. A substantially rectangular supporting plane having rounded ends comprising, in combination, a substantially flat top surface having its marginal edges curved downwardly, a central longitudinal rib on the under surface of said supporting surface, said rib merging gradually into longitudinal recesses formed in the under surface, and said recesses merging with the respective downwardly turned edges at a point above the bottom plane of said rib.

5. A substantially rectangular supporting plane having round ends comprising, in combination, downwardly curved marginal edges surrounding said plane, and a central longitudinal rib on the under surface of said plane merging with longitudinal recesses formed on said under surface between said rib and said curved marginal edges.

6. A substantially rectangular supporting plane having round ends, comprising, in combination, downwardly curved marm'nal edges surrounding said plane, and a central longitudinal rib terminating short of the ends on the under surface of said plane merging gradually with a recess extending therearound between said rib and the downwardly curved marginal edges.

7. A substantially rectangular supporting plane having its marginal edges curved downwardly providing a continuous inclined flange therearound, and means formed in the under surface of said plane and extending longitudinally thereof to equalize the effective lifting force on said wing on each side of the longitudinal center thereof.

8. A substantially rectangular wing for iiying machines, having its ends rounded, comprising, in combination, a downwardly turned portion surrounding said wing, and a oentrally arranged longitudinal, depressed portion on the under surface of said wing forming air pockets of equal capacity thereunder, one on each side of said central portion.

9. In a supporting plane, the combination of, downwardly turned marginal edges surrounding said plane, a depressed central portion in said plane extending below the plane of said marginal edges, and the portion of said plane between said central depressed portion and said marginal edges being depressed to provide air pockets one on each side of said last mentioned depressed portion for stabilizing said plane.

In testimony whereof I aix my signature at l0 South La Salle Street, Chicago, Illinois.

EMMANUEL G. KONTOS. Y 

